Garmin G500, Instructions Manual

Page: 278 / 334

G500/G600 PFD/MFD System 190-00601-00 Rev. M
Instructions for Continued Airworthiness Page 9 of 13

Aircraft with a GMU mounted in the wingtip of metallic aircraft with non-metallic wingtip covers
must inspect the magnetometer installation in accordance with section 8.4.1 of the G500/G600
AML STC Installation Manual.

Aircraft with an ARINC 708 weather radar interfaced to the GDU 620 must inspect the overbraid
to the weather radar in accordance with section 8.4.2 of the G500/G600 AML STC Installation
Manual.

Aircraft with optional GDU 620 dual power bus diodes (see Installation Manual Figure F-2) must
perform a functional check of the diode isolation as follows:
o
Power on Avionics #1 Bus and Avionics #2 Bus. Verify that all avionics are powered on.
o
Power off Avionics #1 Bus only. Verify that both GDU 620 units remain powered on.
Verify that Avionics #1 Bus is unpowered.
o
Power on Avionics #1 Bus and Power off Avionics #2 Bus only. Verify that both
GDU 620 units remain powered on. Verify that Avionics #2 Bus is unpowered.

Non-metallic aircraft with a GSU 75(B) installed must have the GSU 75(B) grounding strap
inspected for signs of lightning damage. If there is evidence of lightning strike damage, replace
the grounding strap using the procedure in appendix N.3 of the G500/G600 AML STC
Installation Manual.
If the Mid-Continent Standby Attitude Indicator (if installed) has not been operated for more than 3
months, charge each battery pack using one of the methods described in section 2.4.
2.10 Application of Protective Treatments
None, N/A.
2.11 Data Relative to Structural Fasteners
Data relative to structural fasteners, such as type, torque, and installation requirements can be found in
section 3 of the G500/G600 AML STC Installation Manual.
2.12 Special Tools
For electrical bonding testing, a milliohm meter is required.
No special tools are required for system checkout. See G500/G600 AML STC Installation Manual listed
in reference documentation in Section 2.1 of this document.
2.13 Additional Instructions
None
2.14 Overhaul Period
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT
will monitor the health of the G500/G600 system. If any LRU indicates an internal failure, the unit may be
removed and replaced. See the troubleshooting section (section 6) contained in the G500/G600 AML
STC Installation Manual, listed under reference documentation in paragraph 2.1 of this document.
2.15 ICA Revision and Distribution
To revise this ICA, a request must be submitted to the ACO or ODA along with the revised ICA. The
ACO or ODA will obtain AEG acceptance, and approve any revision to the Airworthiness Limitations in
Section 1.4. After FAA acceptance/approval, Garmin will release the revised ICA for customer use, and
provide any required notification of the revision.